Abstract
A practical and general method is described and used to derive particular airfoil sections with the desirable flat roof-top characteristics of some optimum profiles. The method is derived from a solution of the inverse airfoil problem, where the dynamic features required of it by the designer are set in the hodograph plane and the airfoil profile, which will realize those design features obtained by a simple process of numerical integration. AH the physical viability criteria are satisfied ab initio and the particular sections calculated exhibit those desirable features by suitably choosing some transformation constants which are fully defined in the hodograph plane. The pressure recovery at the tail end of the upper surface can be helped to develop naturally without separation taking place by making use, if need be, of the process of natural jet injection into the boundary layer at a welldefined station just ahead of an incipient separation point. Some of these so-derived airfoils are described together with their aerodynamic characteristics. The method can also be used to generate high-performance cascade blading for low-speed (incompressible) work, or airfoils, either isolated or in cascades, for use at compressible (subsonic) flow speeds, with little significant structural complexity added.
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